Wing construction.



H. KLECKLER.

WING CONSTRUCTION.

APPLICATION mzo MAR. 31. 1916.

' avwem roz HENRY KLECKLEE.

Patented J an. 14,1919.

3 SHEETS-SHEET i H. KLECKLER. WING CONSTRUCTION.

APPLICATION HLED MAR. 3| I916.

Patented Jan. 14-, 1919.

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amwmtoi H ENEYKLECKLER Quiet/"e13 H. KLECKLER.

WING CONSTRUCTION. APPLICATION man MAR. 3|. 19m.

UNITED STATES PATENT oFFioE.

HENRY KLECKLER, OF BUFFALO, NEW YORK, ASSIGNOR TO CURTISS AEROPLANEMOTOR CORYORATION, A CORPORATION OF N'EW'YORK.

AND

WING consrntrcrron.

To all/whom it may concern:

Be it known that I, HENRY KLEGKLER, a

citizen of the United States, residing at Buffalo, in the county of Erieand State of New York, have invented certain new and useful Improvementsin Wing Construction, of which the following is a specification.

My present invention relates to aircraft equipment and more particularlyto an improved supporting plane or wing of a construction designed tosecure a maximum of rigidity andstrength with a minimum .of weight andresistancecharacteristics essential'to increased speed and liftingefiiciency in a flying machine. I

In describing my invention in detail, reference will be had to theaccompanying drawings wherein like characters of reference designatelike or corresponding parts throughout the several views, in which:

Figure 1 is a plan view of my improved wing structure stripped of itsfabric cover- Fig. 2 is an end view illustrating the general streamlineform of the wing;

Fig. 3 is an enlarged detail transverse sectional view illustrating thewing nose construction Fig. 4 is a plan View illustrating in detail themanner in which one of the compression struts and wing beams are joined;

Fig. 5 is a view somewhat similar to Fig. 3 illustrating in elevationone of the web strips;

Fig. 6 is a viewsomewhat similar to Fig. 4 illustrating the connectionbetween one of I the web strips and the wing beams;

Fig. 7 is an enlarged section on the line 77 of Fig. 1;

Fig. 8 is a similar view on the line 8-8 of Fig. 1; y

Fig. 9 is a similar view on the line 9-9 of Fig. 1;

Fig. 10 is a similar view on the line 10-10 of F1g.-1;

Fig. 11 is an elevation illustrating a modi fied form of compressionstrut;

Fig. 12 is an enlarged cross section on the line 1212 of Fig. 1, and

Fig. 13 is a detail sectionalview illustrating the wing-hingeconstruction.

The wing in its preferred embodiment comprises parallel wing beams 15and 16 Specification of Letters Patent.

mounted to extend laterally of the body of the craft (not shown) in adirection transverse to the line of flight. The rear wing beam 16 isextended slightly beyond the end of the forward wing beam 15 at itsouter end to obtaina somewhat greater spread at the trailing edge withresulting increased lateral stability. Each beam is tapered at'its outeror free end as indicated at 16 that the thickness of the wing at saidouter end may be materially reduced. Wing hinges '17 and 18 are utilizedto effectually secure the wing structure to the fuselage, nacelle orother body structure (not shown). These winghinges are of a.construction best illustrated in Fig. 13 and may be said to consist of-Patented Jan. 14, 1919. Application filed March 31. 1916. Serial No.88.094.

strut of the wing and engaging with the opposite longitudinal edges ofthe wing beam to provide for securement thereto as indicated at 15. Theconnecting portion of each hinge bears against the inner face of the endstrut and accordingly braces and limits movements of the hinge withrespect to .the wing.

While the wing herein illustrated is slightly cambered, and asillustrated in Fig. 2, set at an angle of incidence, it is to beunderstood that such a construction and arrangement is only preferred.

Compression struts, preferably five in number, transversely brace thewing beams, the several struts being disposed in parallelism and atvarying distances apart, the distance between adjacent struts increasingfrom the inner to the outer end of the wing. From said inner endoutwardly, the struts are designated respectively 19, 20, 21,22 and 23,the inner strut having a greater cross-sectional dimension than the nextadjacent strut and so on. the outer strut having the smallestcross-sectional dimension since the strain at the outer end of the wingis less than the strain at the inner end thereof. The inner strut 19,hereinafter referred to as the end strut, like the struts 20 and 21,extends laterally beyond the remote longitudinal edges of the wing beams15 and 16 to secure at the inner end of the wing the desired streamlineform. The outer struts 22 and 23 terminate abruptly at one end and flushwith the rear wing beam 16 to afford at the outer end of the wing anoperating space or jog for the wing flap or aileron (not shown) Theaileron or wing flap will.continue the streamline form of the wing aftat the outer glued or otherwise secured in place.

end thereof and accordingly preclude the formation of vortices at theouter end of the' wing.

The compression struts, exceptthe end strut 19, are constructed alike,each strut comprising a solid web portion 24, the longitudinal top andbottom edges of which engage in longitudinal grooves 25 and 26 formedrespectively in cap-strips 27 and 28 mentioned strips together with theweb portion constitute a compression strut of the face is in evidencewhereby the fabric covering (not shown) for the wing may be glued orotherwise secured in a manner precluding warping and saggingintermediate the several wing structure parts.

Web strips extend parallel with the compression struts and .to a certainextent transversely brace thewing'. Each web strip is laminated asillustrated in Fig. 9 and like the compression struts comprises a webportion 36 and cap strips 37 and 38. The top and bottom longitudinaledges of theweb portion 36 of each web strip is mounted to extend beyondthe top and bottom edges respectively of the wing beams to engage ingrooves therefor formed in the cap strips, the groove in the cap strip37 being desig nated 39 and the groove in the cap strip 38 designated40. Such an arrangement will preclude lateral separation of thelaminations constituting the web strips 36 and, offer to the fabric, asbefore pointed out, a relatively flat securing surface. The relativelydeep web portion of each web strip is such that the cap strips lie flushupon the wing. Each web strip is materially lightened by the formationof lightening holes 41 therein.

Certain of the web strips like the inner compression struts extendbeyond the remote longitudinal edges of the wing beams while.

others terminate flush with the rear wing beam. The outermost extendedweb strip or that portion of the web strip defining the inner end of thejog is diagonally braced as.

indicated at 42 to the wing beam 16 and transversely braced as indicatedat 43 to the The extended Web strip next adjacent thereto.

The transverse bracing strips 43 extend in diverging relation from theoutermost web strip and intersect the diagonal braces 42. Diagonalbraces. 44, 45 and 46 effectually brace the end strut 19 to therespective beams 15 and 16, the braces 44 and 45. engaging with the rearwing beam and the brace 46 with the forward wing beam as illustrated inFig. 1. Transversely extending diverging bracing strips 47 intersect thediagonal brace 44 and engage with the end strut 19 and with the webstrip next adjacent thereto in much the same manner as the transversebrace 43. Both the transverse'brace 43 and the transverse brace 47 bracetheextended tail portion of the wing at apoint equidistant from the wingbeam and the trailing edge of the wing. A trailing edge strip 48(preferably metallic) is mounted to "interconnect the several struts andweb strips which extend aft of the rear wing beam 16. By referring toFig. 12 it w1ll be observed that the web strips and strutscomplementally engage with the trailing edge strip 48 and that the capstrips overhang said strip 48 to which they are secured by a metallicstrip 47 having an overall length sufficient to extend from the jog tothe inner end of the wing. Said strip 47 is-of a shape in cross-sectionto overlap and securely fasten the terminals of the cap-strips to thetail strip of the wing.

A hollowed-out nose strip 49 (curved in cross-section) interconnects theseveral compression struts and web strips at the leading edge of thewing. If desired, bracing strips 50 may extend from the forward wingbeam 15 to the nose strip 49 intermediate adjacent Web strips. Theseveral bracing strips, the compression struts and the web stripseflectually support and brace a veneering strip 51 mounted to extendlongitudinally of the Wing and to engage respectively'the nose strip 49and the wing beam 15, the veneering. l1'1 cross section being curved tosecure a uniform and unbroken engaging surface for the fabric coveringat the top leading edge of the. wing. Upon a careful observaindicated at48 to afford a relatively fiatsecuring surface for the top or uppercapstrips of the web strips and struts.

An angular outer end strip or compression strut 52 is located at theextreme outer end of the wing. Diagonal braces 53 and 54 extend fromeach the beam 15 and thebeam 16 to the mentioned strut 52. Stringers 55longitudinally brace the wing and transversely brace the web-strips, thestring ers engaging with each of the several compression struts and theweb-strips at a point preferably equidistant from the wing beams of thewing.

Compression strains incident to'flight, are

borne by drift wires 56 arranged in pairs within the wing structure 'tointerconnect adjacent struts and to extend diagonally from the forwardend of one strut to the rear end of the strut nextiadjacent -thereto.Turnbuekles 57 may be utilized to effectually tighten the wires 56. Tobrace the wing against strains imposed thereon in alighting, wires 58are provided. The wires 58 like the drift wires 56 interconnect adjacentstruts interiorly of the wing frame. The wires 58, however, intersectthe wires 56 and accordingly oppositely brace the wing. Both'sets ofbracing wires pass through the openings 41 in the web strlps withoutcontact with the strips at any point.

Upon reference to Figs. 3 and 4, it will be observed that the beams 15and 16 are I-formed in cross section to secure lightness without aproportionate decrease in strength. At the points where the compressionstruts engage with the wing beams, the mentioned beams or rather the webportion of each is enlarged as indicated at 59 since the great-.

- est strains incident to flight-are imposed on v a fitting 61 thereto.

the beams at the points where the struts engage therewith.- Blocking 60is interposed between each compression strut and each wing beam toprovide for the securement of The blocking 60 also affords a foundationfor the overhanging portion or portions of the wing post socket 60',since the mentioned'socket as indicated in Fig. 3 is of a size to extendbeyond the opposite longitudinal edges of the wing beam to which it issecured. Each fitting 61 extends laterally beyond the edges of the strutagainst which it is fitted to thus.

provide a means whereby the bracing wires 56 and 58 may be secured tothe beams at the points where the struts intersect or engage. Bolts 62,one of which is an eye-bolt, penetrate the fitting or casting, theblocks and the enlarged portion of the wing beam to secure the former inplace without weakening the beam by reason of openings or bolt-holesformed therein. One of the drift wires of each pair is secured to theeyebolt while the other of said wires is secured to an ear 61 formed inthe fitting 61. A second ear 58 is likewise formed on each fitting toprovide for securement of the wires 58. To further obviate the necessityof weakening the wing beams at any point, the bolt-holes 63 for thesecuring means for the wing post fittings (not shown) are formed in theblocks 60 at opposite sides of the wing beam and notin the wing beamitself as heretofore. Blocks 64,

Bearing blocks 66 afford a-butments for the several strut braces andreceive directly the strains which would otherwise be imposed on thestruts. Each bearing block thus acts as a strain distributing medium inthat the forces or strains exerted on the struts are directedlongitudinally thereof or with the grain rather than transverselythereof and across the grain.

In referring to the modification illustrated in Fig. 11, the I-formedcompressionv struts have been eliminated and tubular compression struts66 substituted instead. The struts 66 are preferably metallic andmounted to engage in sockets 67 secured to the respective wing beams bybolts 68 passing transversely therethrough. In other respects, the wingstructure of the modified wing is the same as that hereinbeforedescribed.

While I have described my invention in detail in its preferredembodiment it will be obvious to those skilled in the art afterunderstanding the invention, that various changes and modifications maybe made therein without departing from the spirit or scope thereof and Iaim in the appended claims to cover all such modifications and changes.v

What is claimed is: M

1. In a wing structure, wing beams, 1aminated web strips interconnectingthe respective beams, and 'cap strips grooved to receive the respectivelongitudinal edges of the several web strips to secure the laminationsagainst separation.

2. In a Wing structure, wing beams, a nose strip, veneeringinterconnecting the forward wing beam and the nose strip to effec-,

tually preclude sagging of the wing covering intermediate said beam andsaid strip, and web strips interconnecting said beam and said nose stripto transversely brace the veneering from beneath.

3. In a wing structure, wing beams, a transversely extending compressionstrut, a bearing block interposed between one end of said strut and saidbeam to receive the compression strains, and a securing means for thementioned block.

4. In a wing structure, wing beams, wing post sockets of a size suchthat the sockets extend beyond the opposite longitudinal edges of therespective beams, blocking interposed between the respective extendedterminals of the several sockets to afford a foundation therefor, andmeans for fastening the blocking to the beams.

5. In a wing structure, wing beams, com pression struts transverselybracing the respective beams, wing fitting blocks mounted upon the beamsat various points throughbeams to which they are connected, a fitting.

out the length thereof, a securing means for the mentioned blocksmounted to transversely penetrate both the blocks and the interposedbetween the terminals of certain of said struts and the blocks securedtothe wing beams, and bracing means for the wing secured to said fitting.I I

6. In a wing structure, wing beams, wing post sockets of a size suchthat the opposite longitudinal edges thereof extend beyond thecorresponding edges of the beams, blocking interposed between therespective extended terminals of the several sockets to afford afoundation therefor and means penetrating the blocking withoutpenetrating the beamsfor fastening the sockets to the beams.

7. In a wing structure, wing beams of I- form in cross sectionthroughout the greater portion of their length, compression struts, andenlargements formed on the respective beams at the points where therespective compression struts engage therewith.

8. In awing structure, Wing beams, and web-strips of a relativelygreater depth than i the thickness of the respective beams to extendrespectively above and below the beams at the terminals of the severalstrips.

9. In a wing structure, a wing beam, a longitudinally channeled nosestrip, means entering the channel of said strip to prevent itsdisplacement relatively to the beam, and

means abutting and extending back from the edges of the nose strip, saidlast men tioned meansafi'ording a foundation for the wing covering ofthe wing characterized by an absence of breaks in its continuity.

10. In a wing structure, wing beams, wing post sockets of a size toextend beyond the opposite longitudinal edges of the respective beams,blocking-interposed between the re spectiveextended terminals of theseveral sockets to afiord a foundation therefor, and a means passingtransversely through the, blocking and through the wing beam to se curethe former against displacementwith respect to said beam.

pression struts connecting the respective beams, diagonally disposedstrut-braces, and

a bearing block interposed between each diagonal brace and itsassociated strut to distribute the strain imposed thereon longi- 5 11.In a wing structure, wing beams, comtend parallel therewith throughoutthe' greater portion of its length, the outer end of the nose stripbeingrearwardly extended to intersect the forward wing beam and con: tact therear wing beam to serve ,conjointly as an'outer edge strip, a trailingedge strip mounted aft of the rear wing beam 'to extend.

parallel therewith, the length of said trail ing edge strip beingconsiderably less thanthe length of the rear wing beam, and web stripsinterconnecting respectively the-nose strip and the forward .wing beam,the two wing beams, and the rear wing beam, and the trailing edge strip,the web strip at the outer end of the wing terminating squarely inalinement with the rear wing beam to provide a jog at the rear outeredge of the" wing defined respectively by the rear wing beam and one ofsaid web strips.

In testimony whereof I afiix my signature HENRY KLECKLER.

